Ceramic matrix composite components with inserts

ABSTRACT

A gas turbine engine is disclosed that includes a compressor, a combustor, and a turbine. The turbine includes a turbine shroud having a blade track formed from a ceramic matrix composite material. The combustor includes a combustor liner formed from one or more ceramic matrix composite tiles.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims priority to and the benefit of U.S. ProvisionalPatent Application No. 62/037,879, filed 15 Aug. 2014, the disclosure ofwhich is now expressly incorporated herein by reference.

TECHNICAL FIELD:

The present invention generally relates to gas turbine engines, and moreparticularly, but not exclusively, to ceramic-containing components usedin gas turbine engines.

BACKGROUND

Gas turbine engines typically include a compressor, a combustor, and aturbine. The compressor compresses air drawn into the engine anddelivers high pressure air to the combustor. In the combustor, fuel ismixed with the high pressure air and the air/fuel mixture is ignited.Products of the combustion reaction in the combustor are directed intothe turbine where work is extracted to drive various components of thegas turbine engine. In operation, ceramic-containing components of boththe combustor and the turbine are exposed to hot, high-pressure air thatresults from the combustor reaction.

Holes are sometimes formed in ceramic-containing components of thecombustor and the turbine that are exposed to the combustion reactionproducts. Such holes can conduct cooling air or accommodate the passageof fasteners through a ceramic-containing component. Forming holesdirectly into ceramic-containing components, however, can presentcomplications. Namely, holes formed directly into ceramic-containingcomponents can expose environmentally sensitive portions of theceramic-containing components to the combustion reaction products, whichmay result in the degradation of the ceramic-containing components overtime.

SUMMARY

The present disclosure may comprise one or more of the followingfeatures and combinations thereof.

According to one aspect of the present disclosure, a turbine shroudadapted for use in a gas turbine engine may include a blade track madefrom ceramic matrix composite materials and an insert. The blade trackmay be formed to include an aperture extending through at least aportion of the blade track. The insert may be formed to include apassageway that extends through the aperture to conduct gasses throughthe aperture while blocking gasses from interacting with surfaces of theblade track that define the aperture.

In some embodiments, the insert may include a liner that forms thepassageway and a retention flange that extends outwardly from the lineralong a side of the blade track that extends away from the aperture toblock movement of the liner through the aperture away from the side ofthe blade track. The aperture formed in the blade track may be a roundbore that extends along an axis, and the passageway formed in the insertmay be coaxial with the aperture. The liner may have an outer diameterthat is greater than a diameter of the aperture so that the insert isinterference fit with the blade track. The turbine shroud may alsoinclude a bond layer between the liner and a side wall that defines theaperture to couple the insert to the blade track. The bond layer may bemade of silicon-containing braze material. The bond layer may be made ofa silicon-containing cement material. The insert may be a monolithiccomponent made from a substantially homogenous material. The materialmay be silicon carbide, or the material may be one of the following:aluminum oxide, zirconium oxide, or rare earth oxide. The material maybe a rare earth silicate, or the material may be one of the following: arare earth aluminate, an alkaline aluminosilicate, or mullite.

According to another aspect of the present disclosure, a combustoradapted for use in a gas turbine engine may include a shell, a linertile made from ceramic matrix composite materials, and an insert. Theshell may be made from metallic materials. The liner tile may be coupledto the shell and formed to include an aperture extending through atleast a portion of the liner tile. The insert may be formed to include apassageway that extends through the aperture to shield surfaces of theliner tile that define the aperture.

In some embodiments, the turbine shroud may further include a fastenerthat extends through the passageway to couple the liner tile to theshell. The insert may include a liner that forms the passageway and aretention flange that extends outwardly from the liner along a side ofthe liner tile that extends away from the aperture to block the linerfrom moving through the aperture away from the side. The aperture formedin the liner tile may be a round bore that extends along an axis and thepassageway formed in the insert may be coaxial with the aperture.

According to yet another aspect of the present disclosure, an assemblyadapted for use in a gas turbine engine may include a component madefrom ceramic matrix composite materials and an insert. The component maybe formed to include an aperture extending through the component from arelatively-high pressure side of the component to a relatively-lowpressure side of the component. The insert may be formed to include apassageway that extends through the aperture to conduct gasses throughthe aperture from the relatively-high pressure side of the component tothe relatively-low pressure side of the component while blocking gassesfrom interacting with surfaces of the component that define theaperture.

In some embodiments, the insert may include a liner that forms thepassageway and a retention flange that extends outwardly from the lineralong the relatively-high pressure side of the component to block theliner from moving through the aperture toward the relatively-lowpressure side of the component. The aperture formed in the component maybe a round bore that extends along an axis and the passageway formed inthe insert may be coaxial with the aperture. The assembly may furtherinclude a fastener that extends through the passageway to couple thecomponent to another part of the assembly.

BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 is a cut-away perspective view of a gas turbine engine;

FIG. 2 is a detail view of a portion of a turbine included in the gasturbine engine of FIG. 1 showing an insert shielding a ceramic turbinecomponent along a hole formed in the component;

FIG. 3 is a cross-sectional view of the portion of the turbine shown inFIG. 2;

FIG. 4 is an exploded perspective assembly view of the ceramic turbinecomponent and the insert included in the portion of the turbine shown inFIGS. 2-3;

FIG. 5 is a cross-sectional view of a portion of a combustor included inthe gas turbine engine of FIG. 1;

FIG. 6 is a detail view of components included in a portion of thecombustor of FIG. 5;

FIG. 7 is a cross-sectional view of a portion of another combustoradapted for use in the gas turbine engine of FIG. 1; and

FIG. 8 is a detail view of components included in a portion of thecombustor of FIG. 7.

DETAILED DESCRIPTION OF THE ILLUSTRATIVE EMBODIMENTS

For the purposes of promoting an understanding of the principles of theinvention, reference will now be made to the embodiments illustrated inthe drawings and specific language will be used to describe the same. Itwill nevertheless be understood that no limitation of the scope of theinvention is thereby intended. Any alterations and further modificationsin the described embodiments, and any further applications of theprinciples of the invention as described herein are contemplated aswould normally occur to one skilled in the art to which the inventionrelates.

Referring now to FIG. 1, a cut-away view of an illustrative aerospacegas turbine engine 10 is shown. The gas turbine engine 10 includes acompressor 12, a combustor 14, and a turbine 16, each of which issurrounded and supported by a metallic case 18. The compressor 12 isconfigured to increase the pressure and the temperature of atmosphericair and to deliver the air at the increased pressure and temperature tothe combustor 14. The combustor 14 mixes the air with fuel, ignites theair/fuel mixture, and delivers the combustion products (i.e., hot,high-pressure gases) to the turbine 16. The turbine 16 converts thecombustion products to mechanical energy (i.e., rotational power) thatdrives the compressor 12 and an output shaft 21. Left-over combustionproducts from the turbine 16 may be discharged to a low pressure airstream, thereby producing thrust.

The turbine 16 includes static turbine vane rings 20, 22 and a turbinewheel assembly 23 having turbine blades 24 positioned between the vanerings 20, 22 as shown in FIG. 3. The turbine vane assemblies 20, 22extend across the flow path of the combustion products delivered fromthe combustor 14 to the turbine 16. The static turbine vane assemblies20, 22 direct the combustion products entering and exiting the turbinewheel assembly 23. The turbine blades 24 are pushed by the combustionproducts to cause the turbine wheel assembly 23 to rotate.

Referring now to FIGS. 2-3, a magnified perspective view of a portion ofa turbine shroud 26 included in the turbine 16 is shown. The turbineshroud 26 blocks combustion products from passing over the turbineblades 24 without pushing the blades 24 to cause rotation of the turbinewheel assembly 23. The turbine shroud 26 includes a turbine blade track28 and a metallic support ring 30 as shown in FIGS. 2-3.

The turbine blade track 28 is illustratively constructed of a ceramicmatrix composite material. In one example, the ceramic matrix compositematerial may include silicon-carbide fibers formed into fabric sheetsand a silicon-carbide matrix. In another example, the ceramic matrixcomposite material may include another ceramic-based material thatincluding reinforcing fibers and a matrix material.

The turbine blade track 28 extends circumferentially to surround theturbine wheel assembly 23 to directly block combustion productsdelivered to the turbine 16 from passing over the turbine blades 24 assuggested in FIGS. 2-3. Combustion products allowed to pass over theturbine blades 24 of the turbine wheel assembly 23 do not cause theblades 24 to rotate, thereby contributing to lost performance within theengine 10.

Cooling apertures 46, sometimes called cooling holes, are formed in theturbine blade track 28 to conduct cooling gasses to hot portions of theturbine blade track 28 as shown in FIGS. 2 and 3. The apertures 46 areillustratively machined into the blade track 28 after the blade track 28has been coated so that a side wall 47 defining the aperture 46 isuncoated and may be susceptible to chemical interaction with coolinggases passing through the apertures 46. Inserts 48 are positioned in theapertures 46 to shield the side walls 47 of the apertures 46 fromcooling gases moving through the apertures 46 thereby blocking chemicalinteractions between the turbine blade track 28 and cooling gases movingthrough the apertures 46.

The metallic support ring 30 is coupled to the metallic case 18 as shownin FIGS. 2-3. The metallic support ring 30 extends circumferentially tosurround the turbine blade track 28 and support the blade track 28relative to the metallic case 18. The metallic support ring 30 includesa pair of axially-extending ledges 32 configured to engage the bladetrack 28 as shown in FIGS. 2-3.

The turbine blade track 28 includes a blade track runner 34 and a pairof hangers 36 as shown in FIGS. 2 and 3. Combustion products deliveredto the turbine 16 cause the plurality of turbine blades of the turbinewheel assembly to rotate along the blade track runner 34. Each of thepair of hangers 36 is interconnected with the blade track runner 34 andextends generally radially-outwardly therefrom as shown in FIGS. 2-3.

The turbine blade track 28 is coupled to the metallic support ring 30such that the pair of hangers 36 of the blade track 28 engage the pairof ledges 32 of the metallic support ring 30 as shown in FIGS. 2-3. Assuch, the pair of hangers 36 and the pair of ledges 32 cooperate to forma retention system when the turbine blade track 28 and the metallicsupport ring 30 are installed within the metallic case 18.

Each of the pair of hangers 36 includes a forward surface 40 and an aftsurface 42 opposite the forward surface 40 as shown in FIG. 3. Thehangers 36 further cooperate with the runner 34 and the support ring 30to define an interior region 44 as shown in FIGS. 2-4. The forwardsurface 40 of the forward hanger 36 is exposed to a higher pressure thanthe aft surface 42. As such, the forward surface 40 is referred toherein as a relatively-high pressure side of the blade track 28, and theaft surface 42 is referred to herein as a relatively-low pressure sideof the blade track 28.

One of the hangers 36 of the turbine blade track 28 is formed to includethe aperture 46 having a diameter D as shown in FIG. 4. The aperture 46is illustratively a round bore that extends along an axis 45. In otherembodiments, the aperture 46 may have an oval, rectangular, or othershape. The aperture 46 extends along an axis 45 through the surfaces 40,42 into the interior region 44. An insert 48 is positioned in theaperture 46 such that the insert 48 extends from the forward surface 40to the aft surface 42. The insert 48 blocks gasses communicated from therelatively-high pressure side to the relatively-low pressure side frominteracting with the side wall 47 that defines the aperture 46.

The insert 48 includes a liner 50 and a retention flange 52 coupled toand extending outwardly from the liner 50 as shown in FIGS. 2-4. Theretention flange 52 illustratively has a cylindrical shape and an outerdiameter D1 that is greater than the diameter D of the aperture 46. Theliner 50 illustratively has a cylindrical shape and an outer diameter D2that is approximately equal to the diameter D of the aperture 46 andless than the diameter D1. As such, the liner 50 is sized to be receivedin the aperture 46.

The insert 48 is positioned in the aperture 46 such that the liner 50 isentirely received in the aperture 46 as shown in FIGS. 2-3. In addition,the insert 48 is positioned in the aperture 46 such that the retainingflange 52 engages the forward surface 40. Engagement between theretaining flange 52 and the planar surface 40 blocks movement of theliner 50 through the aperture 46 and away from the relatively-highpressure side/toward the relatively-low pressure side of the aperture46.

The retaining flange 52 is illustratively sized to withstand pressurefrom the hot, high-pressure gases that is applied to the relatively-highpressure side of the blade track 28. Specifically, the retaining flange52 has a uniform thickness that resists shearing of the retaining flange52 when pressure is applied to the relatively-high pressure side of theblade track 28. In other embodiments, the retaining flange 52 may betapered or chamfered.

The insert 48 is formed to include a passageway 54 that extends throughthe liner 50 and the retaining flange 52 when the insert 48 ispositioned in the aperture 46 as shown in FIG. 3. The passageway 54extends along the axis 45 so that the passageway 54 and the aperture 46coaxially extend along the axis 45. In operation, when the insert 48 ispositioned in the aperture 46, cooling gases are conducted through thepassageway 54. As such, the gasses interact with interior surfaces (notshown) of the liner 50 and the retaining flange 52 included in theinsert 48 rather than the side wall 47 of the aperture 46.

Referring now to FIG. 3, the insert 48 is illustratively a monolithiccomponent (i.e., the liner 50 and the retaining flange 52 are formed asa single, unitary, and integral piece). The insert 48 is illustrativelyconstructed from silicon carbide. In another embodiment, the insert 48may be constructed from at least one of the following: aluminum oxide,zirconium oxide, or rare earth oxide. In yet another embodiment, theinsert 48 may be constructed from a rare earth silicate. In anotherembodiment still, the insert 48 may be constructed from at least one ofthe following: a rare earth aluminate, an alkaline aluminosilicate, ormullite. Finally, in yet another embodiment, the insert 48 may beconstructed from at least one of the following: chromium, cobalt, ormolybdenum. In each of the embodiments described above, the insert 48may be constructed from a material having a substantially homogenouscomposition.

In addition, in each of the embodiments described above, the insert 48may be constructed from a material having a substantially non-homogenouscomposition. In one example, the insert 48 may include a compositebraided tube suspended in a matrix material (e.g. ceramic matrix). Inother examples, the insert 48 may comprise a fiber reinforced oxide or aparticulate reinforced composite. In any case, for each ofabove-described embodiments, the insert 48 is made from a materialproviding an environmental barrier that prevents gasses from interactingwith the ceramic blade track 28 and thereby compromising the mechanicalintegrity of the blade track 28.

A bond layer 56 is located between the liner 50 and portions of the sidewall 47 which defines the aperture 46 as indicated above and shown inFIG. 3. The bond layer 56 is operable to couple the insert 48 to the oneof the hangers 36.

The bond layer 56 is illustratively made of a silicon-containing brazematerial. For example, the bond layer 56 may be made of a silicon-metalsilicide braze material. In other embodiments, the bond layer 56 may bemade of a silicon-containing cement material. For example, the bondlayer 56 may be made of a cement formed from a silicon-based slurry orfrom a pre-ceramic polymer that yields silica, silicate, or siliconoxycarbide. In yet another embodiment, the bond layer 56 may be made ofa material including calcium aluminate.

Though not shown in the figures, the insert 48 may be coupled to the oneof the hangers 36 without the use of an adhesive agent. For instance,the insert 48 may be constructed from a material having a greatercoefficient of thermal expansion than the one of the ceramic hangers 36.Once the insert 48 is positioned in the aperture 46, exposure of theinsert 48 and the one of the hangers 36 to engine operating temperaturesmay cause the insert 48 to expand, thereby urging the liner 50 againstthe side wall 47. As a result of expanding, the diameter D2 of the liner50 may be greater than the diameter D of the aperture 46 so that aninterference fit is formed between the liner 50 and the side wall 47.

Referring to FIG. 5, a combustor 114 of a gas turbine engine 110illustratively includes a plurality of inserts 148. Specifically, theplurality of inserts 148 are positioned in apertures 149 formed in aliner 158 of the combustor 114. When the plurality of inserts 148 arepositioned in the apertures 149, the plurality of inserts 148 shieldportions of the liner 158 that define the apertures 149 from hot,high-pressure gases inside the combustor 114.

The combustor 114 includes a shell 160, the liner 158, fuel nozzles 162,and a heat shield 164 as shown in FIG. 5. The shell 160 is constructedfrom a metallic material and defines an annular cavity 161 that extendsalong an axis 163 as shown in FIG. 5. The liner 158 is arranged insidethe cavity 161 defined by the shell 160 and extends around an annularcombustion chamber 166 in which fuel is ignited to produce the hot,high-pressure gases that drive the gas turbine engine 110. The fuelnozzles 162 are circumferentially arranged around the combustion chamber166 and provide fuel to the combustion chamber 166. The heat shield 164is arranged to protect the shell 160 from the hot, high-pressure gases.

The shell 160 of the combustor 114 illustratively includes an outershell member 168 and an inner shell member 170 that is generallyconcentric with and nested inside the outer shell member 168. Each ofthe outer and inner shell members 168, 170 are coupled to the liner 158as shown in FIG. 5.

The liner 158 of the combustor 114 is illustratively assembled from aplurality of liner tiles 171-174 secured to the shell 160 by a pluralityof metallic fasteners 176 as shown in FIG. 5. In the illustrativeembodiment, each of the liner tiles 171-174 is constructed from aceramic matrix composite material. Each of the liner tiles 171-174 isarranged around the circumference of the outer or inner shell members168, 170. Each of the liner tiles 171-174 includes a body 177 andplurality of axially-extending tabs 178 arranged along anaxially-forward side of a corresponding body 177.

The apertures 149 extend through at least a portion of the liner tiles171-174 as shown in FIGS. 5-6. In the illustrative embodiment, theapertures 149 extend through the axially-extending tabs 178 of the linertiles 171-174. The apertures 149 are aligned with correspondingapertures 151 which are formed in the outer and inner shell members 168,170 of the shell 160. The apertures 149, 151 are aligned and extendparallel to an axis 179 that is perpendicular to the axis 163 as shownin FIG. 6. When the liner tiles 171-174 are coupled to the shell 160using the metallic fasteners 176, the metallic fasteners 176 extendthrough the apertures 149, 151 as shown in FIGS. 5-6.

The plurality of inserts 148 are positioned in the plurality ofapertures 149 as indicated above and shown in FIG. 5. Each of theplurality of inserts 148 is substantially similar to the insert 48 shownin FIGS. 2-4 and described herein. Accordingly, similar referencenumbers in the 100 series indicate features that are common between theinsert 48 and the plurality of inserts 148. The description of theinsert 48 is hereby incorporated by reference to apply to the pluralityof inserts 148, except in instances when it conflicts with the specificdescription and drawings of the inserts 148.

Referring to FIG. 6, one of the plurality of inserts 148 is shownpositioned in the aperture 149 formed in the liner tile 172. The insert148 is positioned in the aperture 149 such that a liner 150 of theinsert 148 is received in the aperture 149. In addition, the insert 148is positioned in the aperture 149 such that a retaining flange 152 ofthe insert 148 extends outwardly from the aperture 149 and engages asurface 180 of the liner tile 172. As such, the retaining flange 152blocks the liner 150 from moving through the aperture 149 and away fromthe surface 180. The insert 148 shields a portion of the surface 180 aswell as other portions of the liner tile 172 that define the aperture149 from the hot, high-pressure gases inside the combustor 114.

The insert 148 is formed to include a passageway 154 that extendsthrough the retaining flange 152 and the liner 150 parallel to the axis179 as shown in FIG. 6. When the insert 148 is positioned in theaperture 149 as shown in FIG. 6, the passageway 154 extends through theaperture 149. As such, the passageway 154 aligns with one of theapertures 151 along the axis 179.

One of the plurality of metallic fasteners 176 extends through thepassageway 154 to couple the liner tile 172 to the inner shell member170 as shown in FIG. 6. The one of the fasteners 176 illustrativelyincludes a head 182, a body 183 coupled to the head 182, and a threadedend 184 coupled to the body 183. The one fastener 176 is positioned inthe passageway 154 and the one aperture 151 such that the head 182engages the retaining flange 152, the body 183 extends through thepassageway 154 and the aperture 151, and the threaded end 184 extends toa point located outside of the inner shell member 170. A metallic nut185 is secured to the threaded end 184 to prevent the fastener 176 frommoving through the aperture 151 and away from the inner shell member170.

Referring to FIG. 7, a combustor 214 of a gas turbine engine 210illustratively includes a plurality of inserts 248. Specifically, theplurality of inserts 248 are positioned in apertures 249 formed in aliner 258 of the combustor 214. When the plurality of inserts 248 arepositioned in the apertures 249, the plurality of inserts 248 shieldportions of the liner 258 that define the apertures 249 from hot,high-pressure gases inside the combustor 214.

The combustor 214 is substantially similar to the combustor 114 shown inFIGS. 5-6 and described herein. Accordingly, similar reference numbersin the 200 series indicate features that are common between thecombustor 114 and the combustor 214. The description of the combustor114 is hereby incorporated by reference to apply to the combustor 214,except in instances when it conflicts with the specific description anddrawings of the inserts 214.

Unlike the liner 158 of the combustor 114, the liner 258 of thecombustor 214 is illustratively assembled from a plurality of ceramicliner tiles 271-272 secured to the shell 260 by a plurality of metallicfasteners 276 as shown in FIG. 7. Unlike the liner tiles 171-174 of theliner 158, the liner tiles 271-272 do not include axially-extendingtabs.

Apertures 249 extend through at least a portion of the liner tiles271-272 as shown in FIGS. 7-8. In the illustrative embodiment, theapertures 249 extend through radially-extending tabs 291 of the linertiles 271-272. The apertures 249 open into apertures 251 which areformed in the outer and inner shell members 268, 270 of the shell 260.The apertures 249, 251 are aligned and extend parallel to an axis 289that is parallel to the axis 163 as shown in FIGS. 5-8. When the linertiles 271-272 are coupled to the shell 260 using the metallic fasteners276, the metallic fasteners 276 extend through the apertures 249, 251 asshown in FIGS. 7-8.

Referring to FIG. 8, one of the plurality of inserts 248 is shownpositioned in the aperture 249 formed in the liner tile 272. The insert248 is positioned in the aperture 249 such that the liner 250 of theinsert 248 is received in the aperture 249. In addition, the insert 248is positioned in the aperture 249 such that the retaining flange 252 ofthe insert 248 extends outwardly from the aperture 249 and engages asurface 290 of the liner tile 272. As such, the retaining flange 252blocks the liner 250 from moving through the aperture 249 and away fromthe surface 290. Unlike the surface 180 of the liner 158, the surface290 extends perpendicular to the axis 163.

The insert 248 is formed to include a passageway 254 that extendsthrough the retaining flange 252 and the liner 250 parallel to the axis289 as shown in FIG. 8. When the insert 248 is positioned in theaperture 249 as shown in FIG. 8, the passageway 254 extends through theaperture 249. As such, the passageway 254 aligns with the aperture 251along the axis 289.

One of the plurality of metallic fasteners 276 extends through thepassageway 254 to couple the liner tile 272 to the inner shell member270 as shown in FIG. 8. The one of the fasteners 276 illustrativelyincludes a head 282, a body 283 coupled to the head 282, and a threadedend 284 coupled to the body 283. The one fastener 276 is positioned inthe passageway 254 and the one aperture 251 such that the head 282engages the retaining flange 252, the body 283 extends through thepassageway 254 and the aperture 251, and the threaded end 284 extends toa point located outside of the inner shell member 270. A metallic nut285 is secured to the threaded end 284 to prevent the fastener 276 frommoving through the aperture 251 and away from the inner shell member270.

While the invention has been illustrated and described in detail in thedrawings and foregoing description, the same is to be considered asillustrative and not restrictive in character, it being understood thatonly the preferred embodiments have been shown and described and thatall changes and modifications that come within the spirit of theinventions are desired to be protected. It should be understood thatwhile the use of words such as preferable, preferably, preferred or morepreferred utilized in the description above indicate that the feature sodescribed may be more desirable, it nonetheless may not be necessary andembodiments lacking the same may be contemplated as within the scope ofthe invention, the scope being defined by the claims that follow. Inreading the claims, it is intended that when words such as “a,” “an,”“at least one,” or “at least one portion” are used there is no intentionto limit the claim to only one item unless specifically stated to thecontrary in the claim. When the language “at least a portion” and/or “aportion” is used the item can include a portion and/or the entire itemunless specifically stated to the contrary.

What is claimed is:
 1. A turbine shroud adapted for use in a gas turbineengine, the turbine shroud comprising a blade track made from ceramicmatrix composite materials and formed to include an aperture extendingthrough at least a portion of the blade track, and an insert formed toinclude a passageway that extends through the aperture to conduct gassesthrough the aperture while blocking gasses from interacting withsurfaces of the blade track that define the aperture.
 2. The assembly ofclaim 1, wherein the insert includes a liner that forms the passagewayand a retention flange that extends outwardly from the liner along aside of the blade track that extends away from the aperture to blockmovement of the liner through the aperture away from the side of theblade track.
 3. The assembly of claim 2, wherein the aperture formed inthe blade track is a round bore that extends along an axis and thepassageway formed in the insert is coaxial with the aperture.
 4. Theassembly of claim 3, wherein the liner has an outer diameter that isgreater than a diameter of the aperture so that the insert isinterference fit with the blade track.
 5. The assembly of claim 3,further comprising a bond layer between the liner and a side wall thatdefines the aperture to couple the insert to the blade track.
 6. Theassembly of claim 5, wherein the bond layer is made ofsilicon-containing braze material.
 7. The assembly of claim 5, whereinthe bond layer is made of a silicon-containing cement material.
 8. Theassembly of claim 2, wherein the insert is a monolithic component madefrom a substantially homogenous material.
 9. The assembly of claim 8,wherein the material is silicon carbide.
 10. The assembly of claim 8,wherein the material is one of the following: aluminum oxide, zirconiumoxide, or rare earth oxide.
 11. The assembly of claim 8, wherein thematerial is a rare earth silicate.
 12. The assembly of claim 8, whereinthe material is one of the following: a rare earth aluminate, analkaline aluminosilicate, or mullite.
 13. A combustor adapted for use ina gas turbine engine, the combustor comprising a shell made frommetallic materials, a liner tile made from ceramic matrix compositematerials that is coupled to the shell and is formed to include anaperture extending through at least a portion of the liner tile, and aninsert formed to include a passageway that extends through the apertureto shield surfaces of the liner tile that define the aperture.
 14. Thecombustor of claim 13, further comprising a fastener that extendsthrough the passageway to couple the liner tile to the shell.
 15. Thecombustor of claim 13, wherein the insert includes a liner that formsthe passageway and a retention flange that extends outwardly from theliner along a side of the liner tile that extends away from the apertureto block the liner from moving through the aperture away from the side.16. The assembly of claim 15, wherein the aperture formed in the linertile is a round bore that extends along an axis and the passagewayformed in the insert is coaxial with the aperture.
 17. An assemblyadapted for use in a gas turbine engine, the assembly comprising acomponent made from ceramic matrix composite materials and formed toinclude an aperture extending through the component from arelatively-high pressure side of the component to a relatively-lowpressure side of the component, and an insert formed to include apassageway that extends through the aperture to conduct gasses throughthe aperture from the relatively-high pressure side of the component tothe relatively-low pressure side of the component while blocking gassesfrom interacting with surfaces of the component that define theaperture.
 18. The assembly of claim 17, wherein the insert includes aliner that forms the passageway and a retention flange that extendsoutwardly from the liner along the relatively-high pressure side of thecomponent to block the liner from moving through the aperture toward therelatively-low pressure side of the component.
 19. The assembly of claim18, wherein the aperture formed in the component is a round bore thatextends along an axis and the passageway formed in the insert is coaxialwith the aperture.
 20. The assembly of claim 19, further comprising afastener that extends through the passageway to couple the component toanother part of the assembly.